• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2002.11a
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• pp.364.2-364
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• 2002

Thermoacoustic oscillation, which stems from phase correlation between unsteady heat release and acoustic fluctuation, can cause severe vibration and incite the excessive local heat transfer inside the rocket engine. It is very important to understand and prevent this phenomenon in the way of rocket engine development. In this study, the propulsion test facility of KSR-III, which is the first liquid propellant rocket developed by KARI, will be introduced. and the characteristics of thermoacoustic ocillation occurred at the facility will be examined.

• Proceedings of the KSME Conference
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• 2001.11b
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• pp.229-234
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• 2001

The thermoacoustic refrigerator bas not only considerable possibility but also commercial usability, because it bas high reliability, lower vibration, no moving part, and can easily be constructed. In this study, the resonance characteristics of the thermoacoustic refrigerator were investigated for better performance, varying length of the resonance tube to 400mm, 500mm, 600mm, 700mm. In order to determine the optimum resonance tube length and the frequency, the $\lambda/4$ thermoacoustic engine and the similar apparatus of Wheatly type refrigerator were constructed. It was used air as a coolant. in the fifth harmonic, it was taken the highest ${\Delta}t$ that was $56.3^{\circ}C$ at 626Hz in 400mm tube with 40mm stack.

• The Journal of the Acoustical Society of Korea
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• v.3 no.1
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• pp.9-15
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• 1984

Thermoacoustic oscillation induced by a heater in a tube with air current is studied theoretically. Linearized perturbation equations are derived in dimensionless form under the assumption that the system is one dimensional. The equation to predict the acoustic power generation from a heating surface is derived and calculated by solving differential equations numerically. The effect of the mean velocity of the air current is illustrated. The energy conversion mechanism is shown by pressure-volume diagram like a heat engine.

• Journal of the Korean Society of Propulsion Engineers
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• v.20 no.1
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• pp.82-89
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• 2016

The unique phenomenon that jet flow kinetic energy is converted to thermal energy through thermoacoustic resonance can be applied for the multiple ignition of liquid rocket engines. The present article includes the basic principle and theory behind the phenomenon as well as major outstanding, previous research works. The thermoacoustic phenomenon is affected by underexpanded jet flow characteristics from a nozzle, geometries of a nozzle and a resonance tube, and chemical composition of jet flow. The paper concludes with discussion what should be considered as crucial issues for the future research on the development of a multiple ignition system of liquid rocket engines.

• Progress in Superconductivity and Cryogenics
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• v.14 no.1
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• pp.34-37
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• 2012

In this paper, configurations and performance of a pulse tube engine (PTE) are investigated. The configuration of PTE is basically designed by using a concept of energy flow. The configurations of PTE are classified as a PTE with two pistons and a PTE with one piston. First, the PTE with two pistons is simulated and the Carnot efficiency is about 41 %. The phase difference of between motion of two pistons located at expander and compressor mainly effects the performance of the PTE. Second, the PTE with one piston is designed. From a concept of analogy, the piston of compressor is replaced by a compliance tube and a resonator. The PTE with one piston is identical with a thermoacousic engine and has the large volume because the compliance tube and resonator are consisted of large volume tubes. Therefore, we will consider each usefulness of the compact PTE with two pistons and the huge PTE with one piston for PTE applications and the judgement of feasibility.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2002.11b
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• pp.636-640
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• 2002

Acoustic coupled combustion instability, which is one of the most undesirable phenomena in the development of liquid propellant rocket engine, can cause serious damage to a rocket itself, and must be avoided by all means. Unfortunately, KSR-III rocket went through combustion instability during engine start at the propulsion test article No.2. To resolve the problem, time sequence (cyclogram) has been changed, and baffle system has been applied. In consequence of change, stable combustion was achieved.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.32 no.9
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• pp.659-668
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• 2008

Combustion instability has been considered as very important issue for developing gas turbine and rocket engine. There is a need for fundamental understanding of combustion instability. In this study, combustion instability was numerically and experimentally investigated in a dump combustor with bluff body. The fuel and air mixture had overall equivalence ratio of 0.9 and was injected toward dump combustor. The pressure oscillation with approximately 256Hz was experimentally obtained. For numerical simulation, the standard k-$\varepsilon$ model was used for turbulence and the hybrid combustion model (eddy dissipation model and kinetically controlled model) was applied. After calculating steady solution, unsteady calculation was performed with forcing small perturbation on initial that solution. Pressure amplitude and frequency measured by pressure sensor is nearly the same as those predicted by numerical simulation. Furthermore, it is clear that a combustion instability involving vortex shedding is affected by acoustic-vortex-combustion interaction. The phase difference between the pressure and velocity is $\pi$/2, and that between the pressure and heat release rate is in excitation range described by Rayleigh, which is obvious that combustion instability for the bluff body combustor meets thermoacoustic instability criterion.